关键词: 变推力火箭发动机;燃料流;再点火;推力控制;燃烧试验

Abstract: This paper outlines a new approach for designing of multi-start aerospace engine. Thenew approach is motivated by analyzing flow, heat-transfer and ignition of flammable fluid in a certaindiameter long tube. The premixed flammable fluid is heated or cooled during its flow through thetube. Therefore, auto ignition and auto distinguish can be realized easily. By controlling the fluid massrate, the engine thrust is also be adjustable.A theoretical analysis model is also established. Analysis results show that the ignitioncharacteristics of the combustor are determined by tube length, diameter, temperature distribution,working condition and premixed flammable fluid property.Successful experiments have been done to prove this new method. Five performance pulses haveben achieved, of which each lasts about two seconds with interval between two pulses of fiveseconds.

Key words: Rocket engine with variable thrust;Fule flow;Reignition;Thrust control;Combustion test